The Boeing Company

Charles Steven Meis

Erik Marc Langhofer

Rachel Malia Darr

Warren Andrew Atkey

Thomas A Campbell

Farhad Nozari

Edward Zielinski

Charles J Fiterman

Alan Thomas Bernier

David Charles Hass

Michael D Bowman

Todd J Germeroth

Jonathan M Cruse

Mark Joseph Clemen, Jr

Casey Y K Ng

George Albert Perry

Jerry Lee Wert

Cris Kevin Bosetti

Scott Hutchinson Gardner

Jon Meis

Hosam E El-Gabalawy

Casey Ng

Anthony D Drury

Bryan Douglas Welsh

David J Lamb

Rachel Meis

Kuohsing E Hung

Carl Hallstrom

David John Shaw

Bryan D Welsh

Mark Joseph Clemen

Casey Y Ng

Jon Christopher Meis

A nozzle configured to receive and disperse a high-pressure fluid or a low-pressure fluid is disclosed. The nozzle includes a nozzle body defining an open end, a closed end, and a side wall connecting the open end to the closed end, where the open end of the nozzle body configured to receive either the high-pressure fluid or the low-pressure fluid. The side wall defines a plurality of low-pressure apertures, a plurality of high-pressure apertures, and a compressible member positioned within the nozzle body. The plurality of high-pressure apertures are positioned downstream from the plurality of pressure apertures. The low-pressure apertures are smaller in size by a predefined ratio when compared to the high-pressure apertures. The compressible member is in an expanded position and blocks the plurality of high-pressure apertures when the open end of the nozzle body receives the low-pressure fluid.

Dual-flow nozzle for dispersing a high-pressure fluid and a low-pressure fluid

Ice detection systems for aircraft and related methods are disclosed. A disclosed example ice detection system includes a thermochromic device to sense a temperature of freestream air relative to a temperature threshold, and a hydrochromic device to sense an amount of moisture in the freestream air relative to a moisture threshold. A controller to detect an icing condition in response to the thermochromic device sensing a temperature that is less than or equal to the temperature threshold and the hydrochromic device sensing an amount moisture that exceeds the moisture threshold.

Ice detection systems for aircraft and related methods

A method and apparatus for simulating icing conditions using a wind tunnel is provided. Water drops are sprayed from a number of nozzles into the wind tunnel. A mist of cryogenic liquid is sprayed into a path of the water drops downwind of the nozzles in the wind tunnel, wherein the mist of cryogenic liquid turns the water drops into ice crystals.

Ice crystal icing condition simulation method and system

Systems and methods are provided for an ice detector with a movable airfoil. The movable airfoil may be airfoil shaped and the ice detector may include an ice detection sensor. The movable airfoil may be adjusted in angle of attack and/or configuration to simulate the pressure gradient experienced by one or more of the wing, fuselage, engine, horizontal/vertical stabilizer, or other component of the aircraft. Sensors may be used to detect the configuration of the aircraft or the components of the aircraft and the configuration of the movable airfoil may then be adjusted to approximate the pressure distribution around the aircraft component. Ice accretion on the movable airfoil may be determined via the data from the ice detector.

Aircraft ice detection systems and methods

A system detects ice on a surface. The system comprises an ultraviolet (UV) light source configured to project light primarily in the UV-A spectrum onto the surface. The system further comprises an optical device configured to capture an image of the surface while the light primarily in the UV-A spectrum is projected by the UV light source. The system further comprises a control device communicatively coupled to the optical device. The control device is configured to receive the image from the optical device and determine whether or not ice is present on the surface based respectively on whether or not visible light induced by the light projected by the UV light source is captured in the image.

Detecting the presence of ice on a surface using ultraviolet light

Aspects of the present disclosure relate to systems and methods for automated fire detection, such as in aircraft galleys, or other areas where power sources may result in fire or smoke. The system includes one or more detectors to monitor for smoke or fire in an aircraft galley. Upon detection of smoke or fire, a signal is sent from the one or more detectors to a controller. In response to the incoming signal, the controller sends a signal to a galley power source. The signal provided to the galley power source ceases the application of power to one or more devices located in the galley, extinguishing the source of the fire or smoke. The controller may also send a notification signal to alert the crew to the potential fire hazard. A method of operation is also disclosed.

Automated galley fire protection system

Disclosed is a temperature sensor for measuring a temperature of a reference material. The temperature sensor includes a thermocouple, spring, and spring housing. The thermocouple is configured to measure the temperature of the reference material. The spring is operably coupled to the thermocouple and the spring housing is configured to accommodate the spring and thermocouple within the spring housing. Additionally, the spring housing is configured to attach to the reference material and the spring applies a force on the thermocouple in a direction towards the reference material.

Temperature sensor

A fire suppression system for a compartment of an aircraft includes a sensor system, at least one valve, and a controller. The sensor system is located within the compartment and includes, at least, a first sensor and a second sensor. The first sensor is configured to detect atmospheric substances within the compartment and the second sensor is configured to detect combustion products within the compartment. The at least one valve is configured for regulating flow of a fire suppressant to the compartment. The controller is configured to control flow of the fire suppressant, via the at least one valve, in response to input from the sensor system. The controller provides instructions to discharge the fire suppressant if the first sensor detects atmospheric substances and the second sensor detects combustion products.

Atmospheric air monitoring for aircraft fire suppression

A method for detecting an icing condition using an apparatus comprising a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Icing condition detection method

An aircraft comprises a fuselage having a compartment, and a fire suppression system for delivering fire suppressant to the compartment. The system includes at least one suppressant concentration sensor located in the compartment, a valve for regulating flow of the fire suppressant to the compartment, and a controller, responsive to the sensor, for controlling the valve to maintain fire suppressant concentration within the compartment at a target concentration.

Aircraft fire suppression

A method includes receiving a plurality of temperature measurements from temperature sensors of an aircraft. The method includes determining whether a first count of one or more first temperature metrics that are within a temperature range is greater than a first threshold. The one or more temperature metrics are derived from the plurality of temperature measurements. The method includes initiating generating an icing output signal when the first count is greater than or equal to the first threshold.

System and method for aircraft ice detection within a zone of non-detection

A method is provided that includes a number of operations performed in real-time during operation of a vehicle. That is, the method may include detecting fog on an interior surface of the window using one or more sensors according to a process, and automatically activating a fog protection system to reduce or prevent fog on the interior surface of the window in an instance in which fog is detected according to the process. For each sensor, the process may include receiving a measurement from the sensor. And from the measurement, the process may include identifying or calculating a dew-point temperature in a compartment of the vehicle including the window to an exterior thereof, and detecting fog on the interior surface of the window in an instance in which the dew-point temperature is near, at, or above a surface temperature of the interior surface of the window.

Automatic activation of a fog protection system onboard a vehicle

In one aspect, methods of detecting ice formation on an aircraft are described herein. In some implementations, a method of detecting ice formation on an aircraft comprises disposing an ice detector on an exterior surface of the aircraft, the ice detector comprising a probe surface and a pyroelectric material layer disposed on at least a portion of the probe surface. The method further comprises generating a charge on a surface of the pyroelectric material layer of the ice detector to increase the local freezing point of water on the surface of the pyroelectric material layer.

Methods and apparatus for detecting ice formation on aircraft

A method and apparatus for detecting an icing condition. The apparatus comprises a piezoelectric material and a vibration detector. The piezoelectric material has a surface proximate to a surface of a vehicle. The piezoelectric material is configured to vibrate. The vibration detector is configured to detect a change in vibrations in the piezoelectric material that indicates a presence of an icing condition on the surface of the piezoelectric material.

Icing condition detection system

A method is provided that includes a number of operations performed in real-time during flight of the aircraft. That is, the method may include monitoring a continuous electrical signal output by a sensor on a surface of the aircraft, where a magnitude of the electrical signal may be related to an amount of ice buildup. The method may include calculating a liquid water content (LWC) value as a function of a rate of change of the electrical signal, and iteratively calculating a total water exposure (TWE) value as a function of the LWC value. The TWE value may represent a total water exposure of the aircraft from a time of an initial event, and may be calculated as a running total over a plurality of iterations. And the method may include performing a remedial or alert action in an instance in which the TWE value reaches a TWE threshold.

Growing community of inventors

Renton, WA, United States of America

Charles Steven Meis